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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Nondestructive test device for evaluation of polyurethane foam sprayed insulation on Saturn S-2 stage
Spray generator produces streams of uniform-size droplets issuing at uniform rate by applying an oscillatory disturbance to free liquid jets. Jets of varying diameters can be grouped together and oscillated as a group to produce simultaneous streams of uniform-size droplets.
Correlation of spray drop size distribution and injector variables
Holograms of reacting and nonreacting droplet sprays for data reduction
External device for liquid spray cooling of gas turbine blades
Aircraft wheel spray drag alleviator for dual tandem landing gear
Polyurethane spray foam insulation system application methods for liquid hydrogen tanks
Liquid diethylcyclohexane /DECH/ sprays detonation propagation in gaseous oxygen, studying drop size effect on steady state development
Orifice length-to-diameter ratio effect on spray mixture uniformity from unlike impinging jets
H alpha solar spray-like prominence ejected in association with bright limb flare, determining knots trajectories and velocities from coronagraph observations
Thin spray film application depths, in the 0.0002 cm to 0.002 cm range, are measured by portable, commercially available, light density measuring device used in conjunction with glass plate or photographic film. Method is automated by using mechanical/electrical control for shutting off film applicator at desired densitometer reading.
Feasibility of spraying flash evaporator as heat rejection device for space shuttle environmental control system
Apparatus for liquid spray cooling of turbine blades
Cold flow analysis of liquid propellant sprays from rocket engine injectors, relating propellant mixing and combustion performance
Spray foam insulation for Saturn S-2 stage, consisting of phenolic honeycomb core composite purged with helium
An analytical and experimental investigation was conducted to perform "proof of principlem experiments to establish the effects of propellant combustion gas velocity on propella'nt atomization characteristics. The propellants were gaseous oxygen (GOX) and Shell Wax 270. The fuel was thus the same fluid used in earlier primary cold-flow atomization studies using the frozen wax method. Experiments were conducted over a range in L* (30 to 160 inches) at two contraction ratios (2 and 6). Characteristic exhaust velocity (c*) efficiencies varied from SO to 90 percent. The hot fire experimental performance characteristics at a contraction ratio of 6.0 in conjunction with analytical predictions from the drovlet heat-up version of the Distributed Energy Release (DER) combustion computer proDam showed that the apparent initial dropsize compared well with cold-flow predictions (if adjusted for the gas velocity effects). The results also compared very well with the trend in perfomnce as predicted with the model. significant propellant wall impingement at the contraction ratio of 2.0 precluded complete evaluation of the effect of gross changes in combustion gas velocity on spray dropsize.
Analytical model formulation, representing performance of spray-combustion device, is based on understanding of atomization, mixing, vaporization, and combustion which occurs in device. Report lists results of correlations of computed values with values obtained from experiments with rocket combustor. Technique offers excellent method for evaluating validity and ranges of applicability of combustion models.
Description of a method for determining the local parameters of the gas mixture resulting from the combustion of sprayed fuel in a gaseous oxidizer. The method is based on the measurement of local static pressures in the gas mixture and does not require the knowledge of the droplet distribution function, drag, and vaporization characteristics. A set of equations with substituted local pressure values is used for calculations. Application of the method is demonstrated on a liquid oxygen-ethanol rocket fuel.